WO2016062155A1 - 阵列多点集爆式脉冲爆震发动机 - Google Patents

阵列多点集爆式脉冲爆震发动机 Download PDF

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WO2016062155A1
WO2016062155A1 PCT/CN2015/087252 CN2015087252W WO2016062155A1 WO 2016062155 A1 WO2016062155 A1 WO 2016062155A1 CN 2015087252 W CN2015087252 W CN 2015087252W WO 2016062155 A1 WO2016062155 A1 WO 2016062155A1
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detonation
fuel
chamber
point
oxidant
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PCT/CN2015/087252
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French (fr)
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赵晴堂
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赵晴堂
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/02—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet
    • F02K7/04—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet with resonant combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/62—Combustion or thrust chambers

Definitions

  • the present invention relates to the field of aerodynamics, and more particularly to a pulse detonation engine for high speed aircraft.
  • the pulse detonation engine has once again become the development direction of aerodynamic technology.
  • the energy of a single knocking will decrease, and the subsonic combustion wave will waste fuel during the process of forming the detonation wave, and the detonation wave will be formed.
  • Long-term, high-frequency knocking is unstable in continuous operation, and this series of problems has hindered the development of pulse detonation engines.
  • the technical problem solved by the present invention is to provide a pulse detonation engine and to provide a working principle and method relating to such an engine to solve the above-mentioned shortcomings in the background art.
  • Array multi-point blasting pulse detonation engine uses electrodes to directly detonate liquid or colloidal mixed fuel and oxidant and multiple small knocks to synthesize a large knock as a working mode and uses a mixture of primers, explosives, thickening
  • the fuel of the agent reduces the waste of fuel, reduces the generation time of the detonation wave, increases the knocking frequency, improves the stability of continuous work, expands the application range, and increases the detonation speed and specific impulse.
  • Array multi-point episodic pulse detonation The machine consists of a detonation tube, a synthetic detonation chamber, an intake control valve, a tail nozzle, a fuel auxiliary mixer, and a controller.
  • the detonation tube is composed of a circular multi-point ignition electrode, a detonation chamber, a detonation nozzle, a rotary mixing valve, a fixed angle rotating motor, and a connecting pipe.
  • the annular multi-point ignition electrode is annular and surrounds the entire detonation chamber to ensure stable continuous ignition.
  • the detonation chamber is a chamber surrounded by an ignition electrode that is filled with fuel and oxidant and directly detonates the mixture of fuel and oxidant by spark ignition through the ignition electrode.
  • the knock nozzle is a converging diverging nozzle connected to the detonation chamber to increase the thrust.
  • the rotary mixing valve is a rotary valve with a mixing function inside the cylinder and a spoiler, which can mix fuel and oxidant.
  • the spoiler is a plurality of s-shaped metal blades mounted in the rotary mixing valve to mix the oxidant and the fuel.
  • the fixed angle rotating electric machine tests a micro motor with a limiter and a rotary spring, and the rotating shaft of the rotating state is rotated to a certain angle, and the rotating spring rotates the rotating shaft to an initial state for controlling the passage of the rotary mixing valve. Broken.
  • the connecting conduit connects the rotary mixing valve to the external fuel and oxidant supply conduit.
  • the synthetic detonation chamber is a cavity equipped with an array of detonation tubes.
  • the detonation tube is arranged opposite to the tail nozzle at a certain angle, and a large detonation wave generated by a plurality of detonation tubes is combined to form a large detonation wave.
  • the large detonation wave pushes the air in the synthetic knock chamber to form a thrust.
  • the intake control valve is a rotary valve controlled by a stepping motor, and can control the intake frequency by controlling the rotational opening and closing frequency of the valve plate, and can also be opened and closed in the PDE and PDRE by controlling the rotation of the valve plate. Choose the appropriate working mode between modes.
  • the tail nozzle is a nozzle that is connected to the convergent expansion of the synthetic detonation chamber and converges to increase the thrust.
  • the fuel-assisted mixer is a plurality of high-power ultrasonic generators attached to a synthetic detonation chamber, and the energy of the ultrasonic waves is used to mix the fuel and the oxidant in the detonation tube.
  • the controller is composed of a main control single chip microcomputer and a control signal amplifier, and controls the fuel and oxidant flow of the engine, the ignition of the ignition electrode, the on/off of the rotary mixing valve, and the on/off control of the intake control valve.
  • the present invention is a novel pulse detonation engine, which uses an electrode to directly detonate a liquid colloid-mixed fuel and an oxidant and uses a plurality of small knocks to synthesize a large knocking operation mode to make the array multi-point detonation type
  • Pulse detonation engines can replace rocket engines and military aero engines.
  • the electrode directly detonates the liquid or colloidal mixed fuel and oxidant to reduce fuel waste, increase the knock frequency, and make the impulse of a single detonation wave not affected by the knock frequency, and expand the application range to be used outside the atmosphere.
  • Multiple small knocks combined with a large knocking mode of operation can more easily control the working state of the engine, not only by controlling the fuel flow to control the engine thrust but also by controlling the number of working detonation tubes to control the thrust.
  • Figure 1 is a schematic view of the structure of the present invention.
  • FIG. 2 is a schematic view showing the structure of the detonation tube of the present invention
  • Figure 3 is a schematic view of the control mechanism of the present invention.
  • the stepping motor 6 drives the valve plate 7 to rotate the intake control valve 1 to open the air to flow into the synthetic detonation chamber 2. After the air is filled, the stepping motor 6 drives the valve plate 7 to rotate the intake control valve 1 to be turned off.
  • the fixed angle rotary electric machine 8 drives the rotary mixing valve 9 to mix the fuel and the oxidant through the spoiler 13 into the detonation chamber 10, the amount of fuel being greater than the amount of the oxidant, and the auxiliary mixer 5 located on the synthetic detonation chamber 2 in the process.
  • the ultrasonic vibration is used to assist in mixing the fuel and oxidant entering the detonation chamber.
  • the annular multi-point ignition electrode 11 When the detonation chamber 10 is filled, the annular multi-point ignition electrode 11 is energized to ignite the fuel and the oxidant is detonated, and the knocking product enters the synthetic detonation chamber 2 through the detonation nozzle 12.
  • the rich detonation product sprayed at a high speed by the plurality of detonation tubes 3 in the synthetic detonation chamber 2 is mixed with the air filled in the synthetic detonation tube 10 to knock again, and the knocking product is driven by the detonation wave to move toward the tail nozzle 4.
  • the engine After the acceleration of the tail pipe 4 is accelerated, the engine is discharged at a high speed to form a thrust.
  • Stepper motor 6 drives valve plate 7 when used outside the atmosphere
  • the rotary intake control valve 1 keeps off the closed synthetic knock chamber 2
  • the fixed angle rotary motor 8 drives the rotary mixing valve 9 to mix the fuel and the oxidant through the spoiler 13 into the detonation chamber 10, the amount of fuel being equal to the amount of the oxidant
  • the auxiliary mixer 5 located on the synthetic detonation chamber 2 during this process assists the mixing of the fuel and the oxidant entering the detonation chamber 10 by ultrasonic vibration.
  • the annular multi-point ignition electrode 11 is energized to ignite the fuel and the oxidant is detonated, and the knocking product enters the synthetic detonation tube 2 through the detonation nozzle 12.
  • the oxygen balance of the knocking products of the plurality of detonation tubes 3 in the synthetic detonation chamber 2 is zero, and the detonation waves emitted from the plurality of detonation tubes 3 synthesize a large detonation wave in the synthetic detonation chamber 2.
  • the engine is discharged at a high speed to form a thrust.
  • Both of the above modes of operation are controlled by the controller 15 to connect the fuel and oxidant pump 17 sensor 16 to the fixed angle rotary motor 8 stepper motor 6 to the annular multi-point ignition electrode 11.
  • the invention uses an electrode to directly detonate a liquid mixed fuel and an oxidant, a plurality of small knocks to synthesize a large knocking operation mode, and adopts a fuel mixed with a primer, an explosive component and a thickener, thereby reducing fuel waste. Reduced the generation time of the detonation wave, increased the knocking frequency, improved the stability of continuous work, expanded the application range, and increased the detonation speed and specific impulse.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Electrolytic Production Of Non-Metals, Compounds, Apparatuses Therefor (AREA)
  • Shaping Metal By Deep-Drawing, Or The Like (AREA)
  • Combined Controls Of Internal Combustion Engines (AREA)

Abstract

一种阵列多点集爆式脉冲爆震发动机，由多个爆震管（3）、合成爆震室（2）、进气控制阀（1）、尾喷管（4）、燃料辅助混合器（5）和控制器（15）组成，合成爆震室是一个装有爆震管阵列的腔体，爆震管相对布设并以一定角度朝向尾喷管方向，爆震管由环形多点点火电极（11）、爆震室（10）、爆震喷管（12）、旋转式混合阀（9）、固定角度旋转电机（8）、连接管道（14）组成。采用混合有起爆药、***成分、增稠剂，可直接引爆的液态或胶体混合的燃料和氧化剂。该爆震发动机可以提高工作稳定性，降低燃料浪费。

Description

阵列多点集爆式脉冲爆震发动机 技术领域
本发明涉及航空动力领域，具体是用于高速飞行器的脉冲爆震发动机。
背景技术
随着科学技术的发展脉冲爆震发动机又一次成为航空动力技术的发展方向。但是由于种种原因脉冲爆震发动机还有很多技术问题没有解决比如随着工作频率的升高单个爆震的能量会降低、形成爆震波的过程中亚音速燃烧波对燃料的浪费、形成爆震波的时间长、高频爆震连续工作不稳定，这一系列的问题阻碍了脉冲爆震发动机的发展。
发明内容
本发明所解决的技术问题在于提供了一种脉冲爆震发动机并提供了有关于这种发动机的工作原理与方法，以解决上述背景技术中的缺点。
本发明所解决的技术问题采用以下技术方案来实现：
阵列多点集爆式脉冲爆震发动机使用电极直接引爆液态或胶体混合的燃料和氧化剂和多个小爆震合成一个大爆震为工作方式并采用一种混合有起爆药、***成分、增稠剂的燃料，降低了燃料的浪费，减少了爆震波生成的时间提高了爆震频率，提高了连续工作的稳定性，扩大了应用范围，提高爆速和比冲。阵列多点集爆式脉冲爆震发动 机由爆震管、合成爆震室、进气控制阀、尾喷管、燃料辅助混合器、控制器六部分组成。
所述爆震管是由环形多点点火电极、爆震室、爆震喷管、旋转式混合阀、固定角度旋转电机、连接管道组成。
所述环形多点点火电极为环形，环绕整个爆震室，确保可以稳定的连续点火。
所述爆震室是一个被环绕点火电极环绕的小室，填充燃料和氧化剂，并通过点火电极以火花式点火法直接起爆燃料和氧化剂的混合物。
所述爆震喷管是一个连接着爆震室的收敛扩张喷管，可以提高推力。
所述旋转式混合阀是一个圆柱体内部带扰流片有混合功能的旋转阀，可以混合燃料和氧化剂。
所述扰流片是多个s形的金属叶片安装在旋转混合阀内可以混合氧化剂和燃料。
所述固定角度旋转电机试一个装有限位器和回转弹簧的微型电动机，通电状态转轴旋转动到一定角度，断电状态回转弹簧会将转轴回转到初始状态，用于控制旋转式混合阀的通断。
所述连接管道连接旋转式混合阀与外部的燃料和氧化剂供应管道。
所述合成爆震室是一个装有爆震管阵列的腔体，爆震管相对布设并以一定角度朝向尾喷管方向，以多个爆震管产生的小爆震波合成一个大爆震波，大爆震波推动合成爆震室内的空气形成推力。
所述进气控制阀是一个由步进电机控制开合的旋转阀片,可以通过控制阀片的旋转开合频率控制进气频率也可以通过控制阀片的旋转开合在PDE和PDRE两个模式之间选择适合的工作模式。
所述尾喷管是一个连接着合成爆震室的收敛扩张再收敛的喷管可以提高推力。
所述的燃料辅助混合器是多个贴在合成爆震室的大功率超声波发生器，利用超声波的能量混合爆震管内的燃料和氧化剂。
所述的控制器是由主控单片机、控制信号放大器组成，控制发动机的燃料和氧化剂流量、点火电极的点火、控制旋转式混合阀的通断、进气控制阀通断。
有益效果：本发明是一种新型的脉冲爆震发动机，用电极直接引爆液态胶体混合的燃料和氧化剂并采用多个小爆震合成一个大爆震的工作方式使得这种阵列多点集爆式脉冲爆震发动机可以代替火箭发动机和军用航空发动机。电极直接引爆液态或胶体混合的燃料和氧化剂可以降低燃料的浪费、提高爆震频率、使得单个爆震波的冲量不受爆震频率的影响、扩大了应用范围可以在大气层外使用。多个小爆震合成一个大爆震的工作方式可以更方便的控制发动机的工作状态，不仅可以通过控制燃料流量控制发动机推力还可以通过控制工作的爆震管的数量控制推力。
附图说明
图1为本发明的结构示意图。
图2为本发明的爆震管结构示意图
图3为本发明的控制机构示意图。
图中：进气控制阀1 合成爆震室2 爆震管3 尾喷管4 辅助混合器5 步进电机6 阀片7 固定角度旋转电机8 旋转式混合阀9 爆震室10 环形多点点火电极11 爆震喷管12 扰流片13 连接管道14 控制器15 传感器16 燃料和氧化剂泵17
具体实施方式
为了使本发明实现的技术手段、创作特征、达成目的与功效易于明白了解，下面结合具体图示，进一步阐述本发明。
在大气层内使用时步进电机6驱动阀片7旋转进气控制阀1打开使空气流入合成爆震室2，空气填充完毕后步进电机6驱动阀片7旋转进气控制阀1关断。固定角度旋转电机8驱动旋转混合阀9使燃料和氧化剂经过扰流片13混合进入爆震室10，燃料的量大于氧化剂的量，在此过程中位于合成爆震室2上的辅助混合器5利用超声波震动辅助混合进入爆震室内的燃料和氧化剂。当爆震室10填充完毕环形多点点火电极11通电点火燃料和氧化剂被引爆，爆震产物通过爆震喷管12进入合成爆震室2。在合成爆震室2内多个爆震管3高速喷出的富燃的爆震产物与合成爆震管10内填充的空气混合再次爆震，爆震产物被爆震波驱动向尾喷管4运动，经过尾喷管4的加速后高速排出发动机形成推力。在大气层外使用时步进电机6驱动阀片7 旋转进气控制阀1保持关断封闭合成爆震室2，固定角度旋转电机8驱动旋转混合阀9使燃料和氧化剂经过扰流片13混合进入爆震室10，燃料的量等于氧化剂的量在此过程中位于合成爆震室2上的辅助混合器5利用超声波震动辅助混合进入爆震室10内的燃料和氧化剂。当爆震室10填充完毕环形多点点火电极11通电点火燃料和氧化剂被引爆，爆震产物通过爆震喷管12进入合成爆震管2。合成爆震室2内的多个爆震管3高速喷出的爆震产物的氧平衡为零，多个爆震管3喷射出的爆震波在合成爆震室2内合成一个大的爆震波，经过尾喷管4加速后高速排出发动机形成推力。以上两种工作方式均由控制器15控制控制器15连接燃料和氧化剂泵17传感器16固定角度旋转电机8步进电机6环形多点点火电极11。
本发明使用电极直接引爆液态混合的燃料和氧化剂、多个小爆震合成一个大爆震为工作方式并采用一种混合有起爆药、***成分、增稠剂的燃料，降低了燃料的浪费，减少了爆震波生成时间提高了爆震频率，提高了连续工作的稳定性，扩大了应用范围，提高爆速和比冲。
以上显示和描述了本发明的基本原理和主要特征和本发明的优点。本行业的技术人员应该了解，本发明不受上述实施例的限制，上述实施例和说明书中描述的只是说明本发明的原理，在不脱离本发明精神和范围的前提下，本发明还会有各种变化和改进，这些变化和改进都落入要求保护的本发明范围内。本发明要求保护范围由所附的权利要求书及其等效物界定。

Claims (10)

  1. 阵列多点集爆式脉冲爆震发动机由多个爆震管、合成爆震室、进气控制阀、尾喷管、燃料辅助混合器、控制器六部分组成,所述合成爆震室是一个装有爆震管阵列的腔体，爆震管相对布设并以一定角度朝向尾喷管方向,所述爆震管是由环形多点点火电极、爆震室、爆震喷管、旋转式混合阀、固定角度旋转电机、连接管道组成。
  2. 阵列多点集爆式脉冲爆震发动机，其特征在于，直接引爆液态或胶体混合的燃料和氧化剂在PERE模式下多个小爆震合成一个大爆震为工作方式在PDE模式下多个含有富燃爆震产物的爆震波在合成爆震管中与空气混合再次爆震,并采用一种混合有起爆药、***成分、增稠剂的燃料和氧化剂改善爆震质量。
  3. 根据权利要求1或2所述阵列多点集爆式脉冲爆震发动机，其特征在于，所述合成爆震室是一个装有爆震管阵列的腔体，爆震管相对布设并以一定角度朝向尾喷管方向，以多个爆震管产生的小爆震波合成一个大爆震波，大爆震波推动合成爆震室内的空气形成推力。
  4. 根据权利要求1或2所述阵列多点集爆式脉冲爆震发动机，其特征在于，可以通过控制燃料和氧化剂的混合比以及进气控制阀是否封闭合成爆震室在PDE和PDRE两种工作模式自由的转换。
  5. 根据权利要求1所述阵列多点集爆式脉冲爆震发动机，其特征在于，所述爆震管是由环形多点点火电极、爆震室、爆震喷管、旋转式混合阀、固定角度旋转电机、连接管道组成。
  6. 根据权利要求2所述阵列多点集爆式脉冲爆震发动机，其特征在于，所述的燃料和氧化剂添加了增稠剂、起爆剂、***、火药添加的增稠剂、起爆剂、***、火药可以是固体粉末也可以是液体，燃料和氧化剂可以是液态可以是胶体，添加时可以选择单独添加增稠剂、起爆剂、***、火药其中的任意成分，也可选择添加其中两种或两种以上的成分。
  7. 根据权利要求1所述阵列多点集爆式脉冲爆震发动机，其特征在于，脉冲爆震发动机机体安装有超声波发生器帮助混合液态的燃料和氧化剂。
  8. 根据权利要求1或2所述阵列多点集爆式脉冲爆震发动机，其特征在于，电极在爆震室内直接引爆液态或胶体混合的燃料和氧化剂，燃料和氧化剂 不通过雾化，而是直接以流动的液体状态混合。
  9. 根据权利要求1或8所述阵列多点集爆式脉冲爆震发动机，其特征在于,使用直接在可以流动液态或液态胶体中直接引爆燃料和氧化剂的混合物。
  10. 根据权利要求1或3所述阵列多点集爆式脉冲爆震发动机，其特征在于，在一个爆震室内两个爆震或多个爆震波以一定角度对冲的方式合成一个大的爆震波向爆震室出口传播。
PCT/CN2015/087252 2014-10-19 2015-08-17 阵列多点集爆式脉冲爆震发动机 WO2016062155A1 (zh)

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